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INSTITUTE OF AERONAUTICAL ENGINEERING
(Autonomous)
Dundigal, Hyderabad -500 043
AERONAUTICAL ENGINEERING
COURSE DESCRIPTORCourse Title COMPUTATIONAL AERODYNAMICS LABORATORY
Course Code AAE109
Programme B.Tech
Semester VI AE
Course Type Core
Regulation IARE - R16
Course Structure
Theory Practical
Lectures Tutorials Credits Laboratory Credits
3 1 4 3 2
Chief Coordinator Mr. G Satya Dileep, Assistant Professor Course Faculty Mr. G Satya Dileep, Assistant Professor
Ms. D.Anitha, Assistant Professor
I. COURSE OVERVIEW:
The aim of this lab complements the computational Aerodynamics course. Students will gain experience in computing aerodynamic problems and understanding flow physics over flat plate, pipe, cylinder, over a wedge and flow over an airfoil. They can gain knowledge in estimating flow analysis for different mach numbers in determining the pressure coefficients over different structural objects and can find lift and drag counters.
II. COURSE PRE-REQUISITES:
Level Course Code Semester Prerequisites Credits
UG AAE003 III Fluid Mechanics and Hydraulics 4
UG AAE004 IV Low Speed Aerodynamics 4
UG AAE008 V High Speed Aerodynamics 4
III. MARKS DISTRIBUTION:
Subject SEE Examination CIA
Examination Total Marks Computational Aerodynamics
Laboratory 70 Marks 30 Marks 100
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IV. DELIVERY / INSTRUCTIONAL METHODOLOGIES:
✘ Chalk & Talk ✘ Quiz ✘ Assignments ✘ MOOCs
✔ LCD / PPT ✘ Seminars ✘ Mini Project ✔ Videos
✔ Open Ended Experiments
V. EVALUATION METHODOLOGY:
Each laboratory will be evaluated for a total of 100 marks consisting of 30 marks for internal assessment and 70 marks for semester end lab examination. Out of 30 marks of internal assessment, continuous lab assessment will be done for 20 marks for the day to day performance and 10 marks for the final internal lab assessment.
Semester End Examination (SEE): The semester end lab examination for 70 marks shall be conducted by two examiners, one of them being Internal Examiner and the other being External Examiner, both nominated by the Principal from the panel of experts recommended by Chairman, BOS.
The emphasis on the experiments is broadly based on the following criteria:
20 % To test the preparedness for the experiment.
20 % To test the performance in the laboratory.
20 % To test the calculations and graphs related to the concern experiment.
20 % To test the results and the error analysis of the experiment.
20 % To test the subject knowledge through viva – voce.
Continuous Internal Assessment (CIA):
CIA is conducted for a total of 30 marks (Table 1), with 20 marks for continuous lab assessment during day to day performance, 10 marks for final internal lab assessment.
Table 1: Assessment pattern for CIA
Component Laboratory
Total Marks Type of Assessment Day to day performance Final internal lab
assessment
CIA Marks 20 10 30
Continuous Internal Examination (CIE):
One CIE exams shall be conducted at the end of the 16th week of the semester. The CIE exam is conducted for 10 marks of 3 hours duration.
Preparation Performance Calculations and Graph
Results and
Error Analysis Viva Total
2 2 2 2 2 10
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VI. HOW PROGRAM OUTCOMES ARE ASSESSED:
Program Outcomes (POs) Strength Proficiency assessed by
PO 1 Engineering knowledge: Apply the knowledge of mathematics, science, engineering fundamentals, and an engineering specialization to the solution of complex engineering problems.
2 Calculations of the observations PO 2 Problem analysis: Identify, formulate, review research
literature, and analyze complex engineering problems reaching substantiated conclusions using first principles of mathematics, natural sciences, and engineering sciences.
3 Calculations of the observations
PO 3 Design/development of solutions: Design solutions for complex engineering problems and design system components or processes that meet the specified needs with appropriate consideration for the public health and safety, and the cultural, societal, and environmental considerations.
3 Lab Practices
PO 4 Conduct investigations of complex problems: Use research-based knowledge and research methods including design of experiments, analysis and interpretation of data, and synthesis of the information to provide valid conclusions.
2 Term observations
PO 5 Modern tool usage: Create, select, and apply appropriate techniques, resources, and modern engineering and IT tools including prediction and modeling to complex engineering activities with an understanding of the limitations.
2 Presentation on real-world problems
3 = High; 2 = Medium; 1 = Low
VII. HOW PROGRAM SPECIFIC OUTCOMES ARE ASSESSED:
Program Specific Outcomes (PSOs) Strength Proficiency assessed by
PSO 1 Professional skills: Able to utilize the knowledge of aeronautical/aerospace engineering in innovative, dynamic and challenging environment for design and development of new products
2 Lab Practices
PSO2 Problem-solving Skills: Imparted through simulation language skills and general purpose CAE packages to solve practical, design and analysis problems of components to complete the challenge of airworthiness for flight vehicles.
2 Guest Lectures
PSO 3 Practical implementation and testing skills: Providing different types of in house and training and industry practice to fabricate and test and develop the products with more innovative technologies
1 Presentation on real-world problems PSO 4 Successful career and entrepreneurship: To prepare
the students with broad aerospace knowledge to design and develop systems and subsystems of aeronautical/aerospace allied systems to become technocrats.
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3 = High; 2 = Medium; 1 = Low
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VIII. COURSE OBJECTIVES :
The course should enable the students to:
I Experience in computing aerodynamic problems and understanding flow physics over the objects.
II Knowledge in estimating flow analysis for different mach numbers.
III Determining the aerodynamic forces like mainly lift and drag.
IV Analyze the errors and cause of errors in computational analysis.
IX. COURSE LEARNING OUTCOMES (CLOs):
CLO
Code CLO’s At the end of the course, the student will have the ability to:
PO’s Mapped
Strength of Mapping AAE109.01 CLO 1 Understand the behavior of flows
around different structured objects.
PO 1 3
AAE109.02 CLO 2 Implement the computational fluid dynamic and computational
aerodynamic fundamentals by using advanced solvers.
PO 1, PO 3, PO 4 3
AAE109.03 CLO 3 Explain the usage of modern tools like ICEM-CFD& FLUENT
PO 3, PO 4, PO 5 3 AAE109.04 CLO 4 Understand the flow properties of flat
plate to demonstrate Reynolds number.
PO 1, PO 2 2
AAE109.05 CLO 5 Understand the aerodynamic properties for flow through circular pipe.
PO 1, PO 2 3
AAE109.06 CLO 6 Understand the aerodynamic properties for flow through cylinder.
PO 1, PO 2 2
AAE109.07 CLO 7 Observe the properties at separation region and wake region of circular cylinder at different Reynolds numbers
PO 2, PO 3 1
AAE109.08 CLO 8 Understand the aerodynamic properties of supersonic flow over a wedge
PO 2, PO 3 1
AAE109.09 CLO 9 Understand the aerodynamic properties of flow over an airfoil.
PO 1, PO 2, PO 3 2 AAE109.10 CLO 10 Differentiate the flow properties
around symmetrical and cambered airfoil
PO 1, PO 2 2
AAE109.11 CLO 11 Analyze the errors and cause of errors in the computational analysis.
PO 2, PO 3 3
AAE109.12 CLO 12 Analyze the coefficient of pressure, lift, drag and moment for different bodies for different flow conditions.
PO 1, PO 2 3
AAE109.13 CLO 13 Determine the shock wave around cone and wedges for supersonic flow conditions..
PO 2, PO 3 3
AAE109.14 CLO 14 Observe flow properties and compare the computation results with
experimental results
PO 2, PO 3, PO 4 2
AAE109.15 CLO 15 Observe the shock waves and 3D relieving effect around the cone at supersonic mach number;
PO 2, PO 3 2
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Code CLO’s At the end of the course, the student will have the ability to:
PO’s Mapped
Strength of Mapping AAE109.16 CLO 16 Solve the One dimensional wave
equation using explicit method of lax equations using finite difference method
PO 2, PO 3, PO 4 2
AAE109.17 CLO 17 Solve the One dimensional heat conduction equation using explicit method
PO 2, PO 3, PO4 3
AAE109.18 CLO 18 Generate the Algebraic and Elliptic grids for computational domains.
PO 1, PO 2, PO 3, PO 4
2 3 = High; 2 = Medium; 1 = Low
X. MAPPING COURSE LEARNING OUTCOMES LEADING TO THE ACHIEVEMENT OF PROGRAM OUTCOMES AND PROGRAM SPECIFIC OUTCOMES:
Course Learning Outcomes
(CLOs)
Program Outcomes (POs) Program Specific
Outcomes (PSOs) PO1 PO2 PO3 PO4 PO5 PO6 PO7 PO8 PO9 PO10 PO11 PO12 PSO1 PSO2 PSO3 PSO4
CLO 1 3
CLO 2 3 3 2 1
CLO 3 3 3 2 2 2 1
CLO 4 2 3 CLO 5 3 3 CLO 6 3 3
CLO 7 3 2
CLO 8 3 2
CLO 9 2 2 3
CLO 10 2 2 1 2
CLO 11 2 3
CLO 12 2 3 2 1
CLO 13 3 3
CLO 14 2 3 3 1 2 1
CLO 15 3 3
CLO 16 2 3 2
CLO 17 3 3 2
CLO 18 1 3 3 2 2 2
3 = High; 2 = Medium; 1 = Low
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XI. ASSESSMENT METHODOLOGIES – DIRECT CIE Exams PO 1, PO 2
PO 3, PO 4, PO 5 SEE Exams
PO 1, PO 2
PO 3, PO 4, PO 5 Assignments - Seminars - Laboratory
Practices
PO 1, PO 2 PO 3, PO 4, PO 5
Student
Viva - Mini Project -
Certification -
XII. ASSESSMENT METHODOLOGIES - INDIRECT
✔ Early Semester Feedback ✔ End Semester OBE Feedback
✘ Assessment of Mini Projects by Experts
XIII. SYLLABUS
LIST OF EXPERIMENTS Week-1 INTRODUCTION
Introduction to computational aerodynamics, the major theories, approaches and methodologies used in computational aerodynamics. Applications of computational aerodynamics for classical aerodynamic’s problems.
Week-2 INTRODUCTION TO GAMBIT
Introduction to gambit, geometry creation, suitable meshing types and boundary conditions.
Week-3 INTRODUCTION TO FLUENT
Introduction to fluent, boundary conditions, solver conditions and post processing results.
Week-4 FLOW OVER A FLAT PLATE
Flow over a flat plate at low Reynolds numbers, observe the boundary layer phenomena, no slip condition and velocity profile inside the boundary layer.
Week-5 FLOW THROUGH PIPE
Flow through pipe at different Reynolds numbers; observe the velocity changes for laminar and turbulent flows.
Week-6 FLOW OVER A CIRCULAR CYLINDER
Flow over a circular cylinder at different Reynolds numbers, observe the properties at separation region and wake region.
Week-7 FLOW OVER A CAMBERED AEROFOIL
Flow over a cambered aerofoil at different velocities, observe flow properties and compare the computation results with experimental results (consider the model from aerodynamics laboratory).
Week-8 FLOW OVER A SYMMETRIC AEROFOIL
Flow over a symmetric aerofoil at different velocities, observe flow properties and compare the computation results with experimental results (consider the model from aerodynamics laboratory).
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Week-9 FLOW OVER WEDGE
Flow over wedge body at supersonic mach number; observe the shock wave phenomena and change of properties across the shock wave.
Week-10 FLOW OVER A CONE
Flow over a cone at supersonic mach number; observe the shock waves and 3D relieving effect.
WeeK-11 CODE DEVELOPEMENT
Solution for the following equations using finite difference method I. One dimensional wave equation using explicit method of lax.
II. One dimensional heat conduction equation using explicit method.
Week-12 CODE DEVELOPEMENT Generation of the following grids
I. Algebraic grids.
II. Elliptic grids.
Reference Books:
1. Hirsch, C., “Numerical Computation of Internal and External Flows: The Fundamentals of Computational Fluid Dynamics”, Vol. I, Butter worth-Heinemann, 2nd edition, 2007.
2. Hoffmann, K. A. and Chiang, S. T., “Computational Fluid Dynamics for Engineers”, Engineering Education Systems, 4th edition, 2000.
3. Patankar, S.V., “Numerical Heat Transfer and Fluid Flow”, Hemisphere Pub. Corporation, 1st edition, 1980.
4. H K Varsteeg, W Malalasekera, “ An Introduction to Computational Fluid Dynamics – The Finite Volume MEthod”, Longman Scientific and Technical, 1st edition, 1995.
XIV. COURSE PLAN:
The course plan is meant as a guideline. Probably there may be changes.
Week No.
Topics to be covered Course Learning Outcomes
(CLOs) Reference
1 Introduction to computational aerodynamics CLO 2 R1: 1.2
2 Introduction to ICEM CFD CLO 3 R4: 3.5
3 Introduction to fluent, boundary conditions, solver conditions and post processing results
CLO 3
R1: 3.4 4 Flow over a flat plate at low Reynolds
numbers
CLO 4
R1: 2.2 5 Flow through pipe at different Reynolds
numbers
CLO 5
R1: 2.4 6 Flow over a circular cylinder at different
Reynolds numbers
CLO6, CLO 7
R1: 4.5 7 Flow over a cambered airfoil at different
velocities
CLO 10, CLO 12
R2: 2.6 8 Flow over a symmetric airfoil at different
velocities
CLO 10, CLO 12
R2: 2.6 9 Flow over wedge body at supersonic Mach
number
CLO 8, CLO 13, CLO 15
R1: 5.2
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No.
Topics to be covered Course Learning Outcomes
(CLOs) Reference
10 Flow over a cone at supersonic Mach number CLO 9, CLO 13, CLO 15 R1: 5.2 11 Solve One dimensional wave equation using
explicit method of lax. One dimensional heat conduction equation using explicit method.
CLO 16, CLO 17
R1:7.2 12 Generation of the Algebraic and Elliptic grids. CLO 18 R1:7.3
XV. GAPS IN THE SYLLABUS - TO MEET INDUSTRY / PROFESSION REQUIREMENTS:
S No Description Proposed
actions
Relevance with POs
Relevance with PSOs 1 To improve standards and analyze
the concepts.
Guest Lectures PO 1, PO 2, PO 4 PSO 1, PSO 2 2 Encourage students to solve real
time applications and prepare towards competitive
examinations.
NPTEL PO 2, PO 3 PSO 1, PSO 2
Prepared by:
Mr. G Satya Dileep, Assistant Professor HOD, AE
